Flight Stability And Automatic Control Nelson Solutions May 2026

∂m / ∂α < 0

Therefore, the aircraft is directionally unstable.

Substituting the given values, we get:

∂n / ∂β > 0

For lateral stability, the following condition must be satisfied:

where xcg is the center of gravity, xnp is the neutral point, and c is the chord length.

SM = (xcg - xnp) / c

Altitude Sensor → Controller → Actuator → Aircraft → Altitude Sensor